Patents by Inventor Christopher L. Ho

Christopher L. Ho has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Active multi-effector control of high pressure turbine clearances
    Patent number: 11473510
    Abstract: A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.
    Type: Grant
    Filed: April 18, 2019
    Date of Patent: October 18, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Joseph Kehoe, Richard P. Meisner, Manuj Dhingra, Patrick D. Couture, Matthew R. Feulner, Brenda J. Lisitano, Christopher L. Ho
  • ACTIVE MULTI-EFFECTOR CONTROL OF HIGH PRESSURE TURBINE CLEARANCES
    Publication number: 20200332726
    Abstract: A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.
    Type: Application
    Filed: April 18, 2019
    Publication date: October 22, 2020
    Inventors: Joseph Kehoe, Richard P. Meisner, Manuj Dhingra, Patrick D. Couture, Matthew R. Feulner, Brenda J. Lisitano, Christopher L. Ho